Numerical computation of gust aerodynamic response for realistic airfoils: Application of Amiet’s theory

Renato Fuzaro Miotto, William Roberto Wolf, Leandro Dantas de Santana

    Research output: Chapter in Book/Report/Conference proceedingConference contributionAcademicpeer-review

    1 Citation (Scopus)

    Abstract

    Current knowledge on the noise generation mechanisms of an airfoil subjected to a turbulent flow indicates that an increment to the airfoil thickness leads to a reduction of the leading-edge noise. This effect is generally attributed to the turbulence distortion occurring close upstream the airfoil leading-edge, combined to a reduction in the magnitude of the aerodynamic transfer function. However, current methodologies do not allow to clearly separate the role of those two distinct physical mechanisms. This paper proposes a technique to compute the aeroacoustic transfer function allowing the study of the leading-edge noise radiated by realistic airfoil geometries. This approach is able to account for trailing-edge aerodynamic back-scattering effects and is valid for blades with large spans, general airfoil geometries, high-frequency perturbations and subsonic compressible flows. The proposed technique deals with the possibility of rewriting the linearized potential flow equations as the Helmholtz formulation leading to a boundary value problem prescribed by the linearized airfoil theory. This problem is calculated by an iterative procedure, where the linearized airfoil theory is solved by a boundary element method (BEM). The proposed numerical methodology is verified against analytical results presented by Amiet’s theory. In this paper we show the importance to account for the effects of a realistic airfoil geometry in the calculation of the aeroacoustic transfer function to improve leading-edge airfoil noise prediction.

    Original languageEnglish
    Title of host publication22nd AIAA/CEAS Aeroacoustics Conference
    PublisherAmerican Institute of Aeronautics and Astronautics Inc. (AIAA)
    ISBN (Print)9781624103865
    Publication statusPublished - 2016
    Event22nd AIAA/CEAS Aeroacoustics Conference 2016 - Lyon, France
    Duration: 30 May 20161 Jun 2016
    Conference number: 22

    Conference

    Conference22nd AIAA/CEAS Aeroacoustics Conference 2016
    CountryFrance
    CityLyon
    Period30/05/161/06/16

    Fingerprint

    Airfoils
    Aerodynamics
    Transfer functions
    Aeroacoustics
    Geometry
    Compressible flow
    Potential flow
    Boundary element method
    Acoustic noise
    Turbulent flow
    Boundary value problems
    Turbulence
    Scattering

    Cite this

    Miotto, R. F., Wolf, W. R., & de Santana, L. D. (2016). Numerical computation of gust aerodynamic response for realistic airfoils: Application of Amiet’s theory. In 22nd AIAA/CEAS Aeroacoustics Conference American Institute of Aeronautics and Astronautics Inc. (AIAA).
    Miotto, Renato Fuzaro ; Wolf, William Roberto ; de Santana, Leandro Dantas. / Numerical computation of gust aerodynamic response for realistic airfoils : Application of Amiet’s theory. 22nd AIAA/CEAS Aeroacoustics Conference. American Institute of Aeronautics and Astronautics Inc. (AIAA), 2016.
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    title = "Numerical computation of gust aerodynamic response for realistic airfoils: Application of Amiet’s theory",
    abstract = "Current knowledge on the noise generation mechanisms of an airfoil subjected to a turbulent flow indicates that an increment to the airfoil thickness leads to a reduction of the leading-edge noise. This effect is generally attributed to the turbulence distortion occurring close upstream the airfoil leading-edge, combined to a reduction in the magnitude of the aerodynamic transfer function. However, current methodologies do not allow to clearly separate the role of those two distinct physical mechanisms. This paper proposes a technique to compute the aeroacoustic transfer function allowing the study of the leading-edge noise radiated by realistic airfoil geometries. This approach is able to account for trailing-edge aerodynamic back-scattering effects and is valid for blades with large spans, general airfoil geometries, high-frequency perturbations and subsonic compressible flows. The proposed technique deals with the possibility of rewriting the linearized potential flow equations as the Helmholtz formulation leading to a boundary value problem prescribed by the linearized airfoil theory. This problem is calculated by an iterative procedure, where the linearized airfoil theory is solved by a boundary element method (BEM). The proposed numerical methodology is verified against analytical results presented by Amiet’s theory. In this paper we show the importance to account for the effects of a realistic airfoil geometry in the calculation of the aeroacoustic transfer function to improve leading-edge airfoil noise prediction.",
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    year = "2016",
    language = "English",
    isbn = "9781624103865",
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    Miotto, RF, Wolf, WR & de Santana, LD 2016, Numerical computation of gust aerodynamic response for realistic airfoils: Application of Amiet’s theory. in 22nd AIAA/CEAS Aeroacoustics Conference. American Institute of Aeronautics and Astronautics Inc. (AIAA), 22nd AIAA/CEAS Aeroacoustics Conference 2016, Lyon, France, 30/05/16.

    Numerical computation of gust aerodynamic response for realistic airfoils : Application of Amiet’s theory. / Miotto, Renato Fuzaro; Wolf, William Roberto; de Santana, Leandro Dantas.

    22nd AIAA/CEAS Aeroacoustics Conference. American Institute of Aeronautics and Astronautics Inc. (AIAA), 2016.

    Research output: Chapter in Book/Report/Conference proceedingConference contributionAcademicpeer-review

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    T2 - Application of Amiet’s theory

    AU - Miotto, Renato Fuzaro

    AU - Wolf, William Roberto

    AU - de Santana, Leandro Dantas

    PY - 2016

    Y1 - 2016

    N2 - Current knowledge on the noise generation mechanisms of an airfoil subjected to a turbulent flow indicates that an increment to the airfoil thickness leads to a reduction of the leading-edge noise. This effect is generally attributed to the turbulence distortion occurring close upstream the airfoil leading-edge, combined to a reduction in the magnitude of the aerodynamic transfer function. However, current methodologies do not allow to clearly separate the role of those two distinct physical mechanisms. This paper proposes a technique to compute the aeroacoustic transfer function allowing the study of the leading-edge noise radiated by realistic airfoil geometries. This approach is able to account for trailing-edge aerodynamic back-scattering effects and is valid for blades with large spans, general airfoil geometries, high-frequency perturbations and subsonic compressible flows. The proposed technique deals with the possibility of rewriting the linearized potential flow equations as the Helmholtz formulation leading to a boundary value problem prescribed by the linearized airfoil theory. This problem is calculated by an iterative procedure, where the linearized airfoil theory is solved by a boundary element method (BEM). The proposed numerical methodology is verified against analytical results presented by Amiet’s theory. In this paper we show the importance to account for the effects of a realistic airfoil geometry in the calculation of the aeroacoustic transfer function to improve leading-edge airfoil noise prediction.

    AB - Current knowledge on the noise generation mechanisms of an airfoil subjected to a turbulent flow indicates that an increment to the airfoil thickness leads to a reduction of the leading-edge noise. This effect is generally attributed to the turbulence distortion occurring close upstream the airfoil leading-edge, combined to a reduction in the magnitude of the aerodynamic transfer function. However, current methodologies do not allow to clearly separate the role of those two distinct physical mechanisms. This paper proposes a technique to compute the aeroacoustic transfer function allowing the study of the leading-edge noise radiated by realistic airfoil geometries. This approach is able to account for trailing-edge aerodynamic back-scattering effects and is valid for blades with large spans, general airfoil geometries, high-frequency perturbations and subsonic compressible flows. The proposed technique deals with the possibility of rewriting the linearized potential flow equations as the Helmholtz formulation leading to a boundary value problem prescribed by the linearized airfoil theory. This problem is calculated by an iterative procedure, where the linearized airfoil theory is solved by a boundary element method (BEM). The proposed numerical methodology is verified against analytical results presented by Amiet’s theory. In this paper we show the importance to account for the effects of a realistic airfoil geometry in the calculation of the aeroacoustic transfer function to improve leading-edge airfoil noise prediction.

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    SN - 9781624103865

    BT - 22nd AIAA/CEAS Aeroacoustics Conference

    PB - American Institute of Aeronautics and Astronautics Inc. (AIAA)

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    Miotto RF, Wolf WR, de Santana LD. Numerical computation of gust aerodynamic response for realistic airfoils: Application of Amiet’s theory. In 22nd AIAA/CEAS Aeroacoustics Conference. American Institute of Aeronautics and Astronautics Inc. (AIAA). 2016